Revision 3 REVISION TRANSMITTAL SHEET This sheet transmits Revision 3 to which: A. Removes the NOTE from the Effectivity section. B. Adds a NOTE to the Reason section. C. Changes SB750-76-06 to SB750-76-07 in the third bullet of the EFFECTIVITY section. D. Changes SB750-76-06 to SB750-76-07 in the ACCOMPLISHMENT instructions. E. Adds (Airplanes that have not incorporated SB750-21-27 and SB750-21-28) to Step 7. F. Changes C9 to C9.1 in the FLIGHT CREW OPERATIONS SUMMARY. NOTE: This revision replaces the original issue and all previous revisions of in their entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by this service bulletin are not affected by this revision. SUMMARY OF REVISIONS Original Issue Mar 22/2002 Revision 1 Oct 14/2002 Revision 2 Aug 1/2005 Revision 3 Jan 20/2010
Revision 2 REVISION TRANSMITTAL SHEET This sheet transmits Revision 2 to. A. Changes the FADEC version from a C8.3 to an upgrade version of C9. B. Adds the requirement SB750-76-06 to be accomplished in conjunction with this service bulletin. C. Adds SB750-76-06 to the REFERENCE section. NOTE: This revision replaces the original issue and any previous revisions of in their entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by this service bulletin are not affected by this revision. SUMMARY OF REVISIONS Original Issue Mar 22/2002 Revision 1 Oct 14/2002 Revision 2 Aug 1/2005
Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Changed the effectivity from -0165, -0168, -0171 and -0172 to -0160 thru -0172. B. Changed the Kit to the -0 Kit. C. Added the -1 Kit for JAA/EASA airplanes. D. Added Step 6, 13, 13F, 13G, 17 and 18 to the ACCOMPLISHMENT INSTRUCTIONS for JAA/EASA airplanes. E. Added flight manual information for JAA/EASA airplanes. NOTE: This revision replaces the original issue of in its entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE OPTIONAL. Airplanes previously modified by this service bulletin that wish to obtain JAA/EASA certification must accomplish Steps 1A, 1B, 1C, 6, 12, 13, 13F, 13G, 14, 16, 17, 18, 20, 21 and 22 before seeking JAA/EASA certification. Airplanes previously modified by this service bulletin that are operating under FAA/JAA/EASA regulations are not affected by this revision. SUMMARY OF REVISIONS Original Issue Mar 22/2002 Revision 1 Oct 14/2002
TITLE POWER PLANT - 400 POUND GROSS WEIGHT AND FIVE PERCENT THRUST INCREASE EFFECTIVITY MODEL SERIAL NUMBERS 750 (Citation X -0160 thru -0172 The equivalent of this service bulletin has been incorporated on production airplanes -0173 and On. This service bulletin must be accomplished at a Cessna owned Citation Service Center. SB750-79-01 must be accomplished prior to or in conjunction with this service bulletin. SB750-76-07 must be accomplished in conjunction with this service bulletin. The Nordam Group Service Bulletin 7000CX 78-2 must be accomplished in conjunction with this service bulletin. Rolls-Royce Service Bulletin AE3007C-72-186 must be accomplished in conjunction with this service bulletin. See planning information in Rolls-Royce Service Bulletin AE3007C-72-186 for other Rolls-Royce service bulletin prerequisites. REASON To provide a 400 pound gross weight and associated five percent take-off thrust increase. In addition to the take-off thrust increase, the mid altitude climb thrust is increased when the anti-ice is turned off. NOTE: The incorporation of this service bulletin upgrades the engines to AE3007C1 status. DESCRIPTION The gross weight and thrust increase is accomplished with changes (modifications) to the engine & oil tank relief drain hardware, FADEC software, Honeywell Primus 2000 software and EICAS indication, thrust reverser and bleed air lines. The take-off thrust increase is accomplished with changes to the FADEC thrust schedule. The five percent thrust increase occurs from sea level up to 5000 ft., phasing out linearly from 5000 to 8000 ft. Climb thrust is increased at mid-level altitudes on warmer than standard days to provide improved multi-engine, anti-ice off climb performance. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 1 of 8 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2002
COMPLIANCE OPTIONAL. This service bulletin may be accomplished at the discretion of the owner. A service bulletin published by Cessna Aircraft Company may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service bulletin, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service bulletin kit. Only with written authorization from Cessna Aircraft Company can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service bulletin only as approved and published. 4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraft serial numbers identified in the Effectivity section of the bulletin. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Cessna Aircraft Company is authorized to make or apply any changes to a Cessna-issued service bulletin, service letter, or flight manual supplement without prior written consent from Cessna Aircraft Company. Cessna Aircraft Company is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Cessna-owned Citation Service Center. FLIGHT CREW OPERATIONS See the attached Flight Crew Operations Summary. APPROVAL FAA/JAA/EASA approval has been obtained on technical data in this publication that affects airplane type design. This information shall be considered an amendment to the Cessna Manufacturer's Maintenance Manual. MANPOWER MATERIAL - Cost and Availability WORK PHASE MAN-HOURS Modification * PART NUMBER AVAILABILITY COST -0 * * -1 * * * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 2
CONSUMABLE MATERIAL In addition to the above kit(s), the following materials, or equivalent, are required for the accomplishment of this service bulletin. NAME NUMBER MANUFACTURER USE Tape F840021 Citation Parts Distribution 7121 Southwest Blvd. Wichita, KS 67215 Phone: 1-800-835-4000 (Domestic) 1-316-517-7542 (International) Insulation G441858 Citation Parts Distribution 7121 Southwest Blvd. Wichita, KS 67215 Phone: 1-800-835-4000 (Domestic) 1-316-517-7542 (International) Install insulation on tube assemblies. Install insulation on tube assemblies. TOOLING None CHANGE IN WEIGHT AND BALANCE MODEL 750 (FAA) 750 (JAA/EASA) WEIGHT INCREASE 0.38 1.08 RESULTANT MOMENT 192.34 524.90 MOMENT/100 1.92 5.25 REFERENCES Cessna Model 750 Citation X Maintenance Manual Cessna Citation Service Bulletin SB750-79-01 Cessna Citation Service Bulletin SB750-76-07 The Nordam Group Service Bulletin 7000CX 78-2 Rolls-Royce Service Bulletin AE 3007C-72-186 Cessna Model 750 Interior Maintenance Manual and Illustrated Parts Catalog NOTE: The latest revision of each of the following engineering drawings and all applicable amendments, drawing change notices, and parts lists released at the time of modification must be used. DOCUMENT NUMBER TITLE 6795002 PROPULSION MOD C TO C1 CONVERSION 9500400 CITATION X AVIONICS SYSTEMS PROGRAMMING REFERENCE 9554011 NOSE AVIONICS EQUIP INSTALLATION 9590010 PHASE 7 AVIONICS FIELD MOD 6791232 (JAA/EASA airplanes only) JAA/EASA BPC SERVICE AIR MOD Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 3
PUBLICATIONS AFFECTED Cessna Model 750 Citation X FAA Approved Airplane Flight Manual 75FMA-00 or later Revision Cessna Model 750 Citation X FAA Approved Airplane Flight Manual 75EUA-00 or later Revision Cessna Model 750 Citation X FAA Approved Airplane Flight Manual 75EUMA-00 or later Revision Cessna Model 750 Citation X FAA Approved Weight and Balance Manual 75WBA-00 or later Revision Cessna Model 750 Citation X Maintenance Manual Cessna Model 750 Citation X Illustrated Parts Catalog ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the batteries. (2) Disconnect external electrical power. C. Attach maintenance warning tags stating: DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROCESS to the following: (1) Airplane batteries (2) External power receptacle D. Disconnect external hydraulic power and attach maintenance warning tags to the hydraulic service doors stating: DO NOT CONNECT HYDRAULIC POWER - MAINTENANCE IN PROCESS. E. Remove the left and right upper and lower cowls. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) 2. Do The Nordam Group Service Bulletin 7000CX 78-2. 3. Do Rolls-Royce Service Bulletin AE 3007C-72-186. 4. Do Cessna Citation Service Bulletin SB750-79-01. 5. Do Cessna Citation Service Bulletin SB750-76-07 (perform the AE3007C1 upgrade). 6. Modify the airplane to comply with the requirements of the following Cessna Engineering Drawings. A. 6795002 Propulsion Mod C To C1 Conversion. NOTE: Refer to the Maintenance Manual, Chapter 36, Bleed Air Couplings - Maintenance Practices for seal replacement procedures before performing Flagnotes 4, 5 and 6. NOTE: Accomplishing Cessna Citation Service Bulletin SB750-79-01 is equivalent to accomplishing Flagnote 3 of 6795002. B. 9590010 Phase 7 Avionics Field Mod. 7. (JAA/EASA airplanes only) (Airplanes that have not incorporated SB750-21-27 and SB750-21-28) Modify the cabin and baggage door seal service air systems. A. Remove access panels 311CL and 313CB. (Refer to the Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.) B. Remove interior components as necessary to access the panel described in the next step. (Refer to the Interior Maintenance Manual and Illustrated Parts Catalog.) C. Remove the access plate located just aft of the cabin entry door and just above the cabin floorboards. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 4
D. Modify the cabin and baggage door service air systems to comply with the requirements of Cessna Engineering Drawing 6791232. 8. Remove maintenance warning tags from the external power receptacle and connect external electrical power. 9. Do the following to check operation of the IC-800's. A. Apply avionics power and allow time for all systems to initialize. B. Do the following. (1) Make sure that CONFIG MISMATCH 1-2 is not shown on the engine indicating and crew alerting system (EICAS) display. (2) MakesurethatnoPrimus2000systemfailuremessagesareshownonEICASthatcannotbe accounted for. C. Enter integrated maintenance test (IMT) and make sure that the Integrated Avionics Computer (IAC) configuration strap number 71 is cut on both the left and right configuration modules. 10. Do the following to check operation of the data acquisition units (DAU's). A. Make sure there are no DAU fail messages on EICAS. B. Make sure all indications on the EICAS display are valid. C. Press the DAU 1 REV and DAU 2 REV buttons. D. Repeat Steps A and B. 11. Do the following to check operation of the thrust reversers. A. Do a thrust reverser test. (Refer to the Maintenance Manual, Chapter 78, Thrust Reverser - Adjustment/Test.) B. Do a thrust reverser emergency stow test. (Refer to the Maintenance Manual, Chapter 78, Thrust Reverser - Adjustment/Test.) C. Do a thrust reverser deploy limit test. (Refer to the Maintenance Manual, Chapter 78, Thrust Reverser - Adjustment/Test.) 12. Remove external electrical power. 13. Remove maintenance warning tags and connect the airplane batteries. 14. Start the left and right engines. (Refer to the FAA approved Airplane Flight Manual 75FMA-00, 75EUA-00 or 75EUMA-00 or later Revision, as appropriate.) A. Make sure that the N1 target on the EICAS matches that shown in Section Four of the FAA approved Airplane Flight Manual 75FMA-00, 75EUA-00 or 75EUMA-00 or later Revision, as appropriate. B. Make sure that the engines achieve takeoff power shown in Section Four of the FAA approved Airplane Flight Manual 75FMA-00, 75EUA-00 or 75EUMA-00 or later Revision, as appropriate. C. Make sure that the standby engine indicator shows the same engine information as EICAS. D. Move the L ENG BLD AIR and R ENG BLD AIR switches to the HP/LP position. E. Make sure there are no leaks as a result of incorporating Cessna Engineering Drawing 6795002. F. (JAA/EASA airplanes only) Make sure there are no leaks as a result of incorporating Cessna Engineering Drawing 6791232. G. (JAA/EASA airplanes only) Make sure that the CABIN DOOR SEAL and BAGGAGE DOOR SEAL messages are not present on the Engine Indicating and Crew Alerting System (EICAS). 15. Shutdown the airplane. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 5
16. Install the left and right upper and lower engine cowlings. (Refer to the Maintenance Manual, Chapter 71, Engine Cowlings - Maintenance Practices.) 17. (JAA/EASA airplanes only) Install access panels 311CL and 313CB. (Refer to the Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.) 18. (JAA/EASA airplanes only) Install the access plate located just aft of the cabin entry door and just above the cabin floorboards. 19. (JAA/EASA airplanes only) Install interior components that were removed for access to the access plate installed in the above step. (Refer to the Interior Maintenance Manual and Illustrated Parts Catalog.) 20. Give the Flight Crew Operations Summary, included with this service bulletin, to the crew to inform them of the operational changes resulting from incorporation of this service bulletin. 21. Make sure that the following publications are given to the flight crew. A. Cessna Model 750 Citation X FAA Approved Airplane Flight Manual 75FMA-00, 75EUA-00 or 75EUMA-00 or later Revision, as appropriate. B. Cessna Model 750 Citation X FAA Approved Weight and Balance Manual 75WBA-00 or later Revision. 22. Make an entry in the airplane logbook stating this service bulletin has been accomplished. 23. Fill out and forward a Maintenance Transaction Report indicating compliance to: CESCOM, P.O. Box 7706, Wichita, KS 67277. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 6
MATERIAL INFORMATION NOTE: The parts included in this service bulletin cover installation for one airplane. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -0 1 Kit, consisting of the following parts: AN833-4J 1 Elbow AN924-4J 1 Nut MS9385-04 1 O-ring Same Discard MS9068-230 2 O-ring Same Discard W932-24F 8 Seal Same Discard W932-40B 2 Seal Same Discard 6714393-47 1 Tube Assembly 6714393-7 Discard 6755402-45 1 Tube Assembly 6755402-5 Discard 6755402-46 1 Tube Assembly 6755402-6 Discard 6755402-49 1 Tube Assembly 6755402-29 Discard 6755402-50 1 Tube Assembly 6755402-30 Discard 6755402-51 1 Tube Assembly 6755402-33 Discard 6755402-52 1 Tube Assembly 6755402-30 Discard 1 Instructions NOTE: In addition to the -0 Kit, the following will be required for JAA/EASA airplanes. NEW P/N QUAN- TITY -1 1 Kit, consisting of the following parts: MS21043-4 9 Nut NAS1149F0463P 18 Washer NAS6204-50D 9 Bolt W991-40TE 2 Coupling 6791232-3 3 Restricted Fitting Assembly 91473 1 Zinc Filter Bowl KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 7
NOTE: In addition to the -0 and -1 Kit, the following is to be returned to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, KS 67215 USA. These parts will be upgraded to the required modification level and returned to the owner/operator for installation. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION 10485N04M03 1 Standby Engine Indicator 10485N03M03 Return to Cessna for upgrade 7013348-943 2 Data Acquisition Unit (DAU) 7013348-928 Return to Cessna for upgrade 7017300-31424 (FAA Certified) 7017300-31434 (JAA/EASA Certified) 7017300-31494 (FAA Certified) 7017300-31514 (JAA/EASA Certified) 2 IC-800 7017300-31404 Return to Cessna for upgrade 2 IC-800 7017300-31404 Return to Cessna for upgrade 2 IC-800 (Phase 7) 7017300-31484 Return to Cessna for upgrade 2 IC-800 (Phase 7) 7017300-31464 Return to Cessna for upgrade Owner/Operators must schedule in advance to have the existing air data computer upgraded. Return the removed component to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, Kansas 67215, USA. Owner/Operators must contact Citation Parts Distribution, telephone number 1-800-835-4000 (Domestic) or 1-316-517-7542 (International) or telefax 316-517-7711 for advance scheduling. Instructions for shipping will be provided by the scheduler. We estimate a current turnaround time of approximately five (5) days. Mar 8/2002 750-71-10 Revision 3 - Jan 20/2010 Page 8
ATTACHMENT FLIGHT CREW OPERATIONS SUMMARY This summary provides additional information for the flight crew regarding operational changes as a result of accomplishment of this service bulletin. Please remove this summary from the service bulletin and give it to the flight crew. This summary is informational only and does not supersede any information in the FAA Approved Airplane Flight Manual. 1. Modifications have been made to allow a 400 pound gross weight and a five percent take-off thrust increase. 2. The new engine model designation is Rolls-Royce AE3007C1, the FADEC software version is C9.1 and the Honeywell Primus 2000 software version is Phase 7. 3. The thrust increase is accomplished with changes to the take-off and climb thrust schedule in FADEC software C9.1. The 5% thrust increase occurs from sea level (ISA +27C) up to 5000 ft. (ISA), phasing out linearly from 5000 to 8000 ft. The improved multi-engine climb performance is at mid-level altitudes on ISA & ISA+20C days. It does not apply to anti-ice ON thrust schedules. 4. Phase 7 EICAS changes support the increased take-off and max continuous ITT limits and oil pressure limits. EICAS indication and standby engine indicator changed to support the higher ITT limits. Take-off limit increased - Fixed segment red-line changes from 888 to 907 C. Maximum Continuous limit increased from 850 to 857 C - Vertical amber bands change from 850-888 C to 857-907 C. Standby engine instrument supports the new ITT limit - digits will flash above 907 rather than 888 C. Added an amber transient oil pressure range from 95 to 155 psi allowing operation above the normal 95 psi steady state oil pressure limit for two minutes or less. 5. FADEC C9 supports Time Limited Dispatch (TLD) which allows for operation for a specified time interval with certain FADEC faults present. TLD requirements are specified in Chapter 5 of both Cessna and Rolls-Royce Maintenance Manuals. Time limited faults are annunciated by white Aircraft Maintenance message and accessed through Honeywell maintenance display page. TLD is conservatively based on a fixed maintenance inspection interval to check for and clear all FADEC faults every 270 flight hours. FADEC faults with an amber CAS message are considered "No-Dispatch" and must be fixed before dispatch. 6. Refer to the Cessna Model 750 Citation X FAA approved Airplane Flight Manual 75FMA-00, 75EUA-00 or 75EUMA-00, or later revision as appropriate, and the FAA approved Weight and Balance Manual 75WBA-00, or later revision for a complete description of operational changes resulting from incorporation of this service bulletin.
TITLE SUPPLEMENTAL DATA POWER PLANT - 400 POUND GROSS WEIGHT AND FIVE PERCENT THRUST INCREASE EFFECTIVITY MODEL SERIAL NUMBERS 750-0160 thru -0172 This service bulletin must be accomplished at a Cessna owned Citation Service Center. SB750-79-01 must be accomplished prior to or in conjunction with this service bulletin. The Nordam Group Service Bulletin 7000CX 78-2 must be accomplished in conjunction with this service bulletin. Rolls-Royce Service Bulletin AE3007C-72-186 must be accomplished in conjunction with this service bulletin. See planning information in Rolls-Royce Service Bulletin AE3007C-72-186 for other Rolls-Royce service bulletin prerequisites. The equivalent of this service bulletin has been accomplished on production airplanes -0173 and On. MANPOWER WORK PHASE Modification MAN-HOURS As Required MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * * -1 * * * Please contact Citation Parts Distribution for current cost and availability of parts listed in this service bulletin. Phone at 1-800-835-4000 (Domestic) or 1-316-517-7542 (International). Send Email to: citationparts@cessna.textron.com or telefax at 1-316-517-7711. Based on availability and lead times, parts may require advanced scheduling. In cases where the required part(s) are available as exchange, order the exchange part and, upon completion, expedite the return of the removed core to avoid return penalties. Contact the Citation Parts Distribution Sales Desk for availability of exchange parts. Mar 8/2002 750-71-10 Revision B - Jan 20/2010 Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2002